Projectile or rocket preferably with unfolded tail unit

ABSTRACT

A projectile, preferably a rocket with an unfoldable tail or rudder fin unit with a plurality of guiding fins movable between a storage position extending tangentially along the projectile to a flight position extending radially of the projectile longitudinal axis. A sliding sleeve is arranged in the projectile for engagement with pivot levers on the guiding fins so as to maintain the guiding fins in the storage position until a predetermined instant in the launching of the projectile, at which time the sliding sleeve engages the pivot levers to unfold the fins and force them into their flight position. The sliding sleeve is maintained in a first arresting position for holding the pivot levers and guide fins in the storage position by means of a connecting disk abutting the rear end of the sleeve. This connecting disk is attached to the projectile in such a manner that ignition of propellant charge means disposed rearwardly of the disk cause a disconnection of the disk with respect to the projectile, with a consequent falling away of the disk after the projectile has left a gun barrel so that a rocket engine disposed forwardly of the disk can operate unimpeded by the disk. The disk is provided with a throttle opening for accommodating transfer of propellant charge gases to ignite the rocket cruising engine and to assist a compression spring in moving the sleeve rearwardly to unfold the guiding fins. Preferred embodiments utilize the disk arrangement for accommodating the propellant charge initial acceleration and the later operation of the cruising engine with or without the further inclusion of the sliding sleeve for controlling foldable guide fins. Other features include a cup spring arrangement for holding a warhead detonator in position between detachably connected parts of the projectile, as well as novel conduit means for transferring the propellant charge gases to an ignition element for the crusing engine.

United States Patent IIJI Voss et al.

l l PROJECTlLE ()R ROCKET PREFERABLY WlTH UNFOLDED TAIL UNIT [75] Inventors: Alfred Voss, Cologne; Manfred Strunk, Neuenrade; Heinz Kroschel, Troisdorf-Sieglar; Heinz Wilhelm Kreutz, TroisdorFOberlar, all of Germany [73l Assignee: Dynamit Nobel Aktiengesellschaft,

Germany [22I Filed: June 4, I973 [2i] Appl No 366,755

[30] Foreign Application Priority Data June 3. i972 Germany. t i v v a i i i 22Z7l04 [52] US. Cl i i v i i 244/327; 244/328 [5 l] Int. Cl. i i i a v v v i i i F42B 13/32 [58] Field of Search i 102/493. 702 GA;

Primary E.runiilierVerlin R. Pendegrass Attorneyv Agent. or Firm-Craig & Antonelli [57] ABSTRACT A projectile. preferably a rocket with an unfoldable ll; "MI/M 1 11 l Nov. 25, 1975 tail or rudder fin unit with a plurality of guiding fins movable between a storage position extending tangentially along the projectile to a flight position extending radially of the projectile longitudinal axis. A sliding sleeve is arranged in the projectile for engagement with pivot levers on the guiding fins so as to maintain the guiding fins in the storage position until a predetermined instant in the launching of the projectile at which time the sliding sleeve engages the pivot levers to unfold the fins and force them into their flight position The sliding sleeve is maintained in a first arrest ing position for holding the pivot levers and guide this in the storage position by means of a connecting disk abutting the rear end of the sleeve This connecting disk is attached to the projectile in such a manner that ignition of propellant charge means disposed rearwardly of the disk cause a disconnection of the disk with respect to the projectile, with a consequent falling away of the disk after the projectile has left a gun barrel so that a rocket engine disposed forwardly of the disk can operate unimpeded by the disk. The disk is provided with a throttle opening for accommodating transfer of propellant charge gases to ignite the rocket cruising engine and to assist a compression spring in moving the sleeve rearwardly to unfold the guiding fins. Preferred embodiments utilize the disk arrange ment for accommodating the propellant charge initial acceleration and the later operation of the cruising engine with or without the further inclusion of the sliding sleeve for controlling foldable guide fins Other features include a cup spring arrangement for holding a warhead detonator in position between detachably connected parts of the projectile, as well as novel conduit means for transferring the propellant charge gases to an ignition element for the crusing engine.

34 Claims, 10 Drawing Figures U.S. Patent Nov. 25, 1975 Sheet 1 of3 3,921,937

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US. Patent Nov. 25, 1975 FIG. 5

Sheet 2 of 3 U.S. Patent Nov. 25, 1975 Sheet3of3 3,921,937

PROJECTILE OR ROCKET PREFERABLY WITH UNFOLDED TAIL UNIT BACKGROUND AND SUMMARY OF THE INVENTION This invention relates to a projectile or rocket of the type with an unfoldable tail or control flap .unit. The fins or wings which serve as control flaps for this type of projectile can be unfolded about axes arranged at right angles to the longitudinal axis of the projectile or rocket, tangentially to the rudder or control flap unit carrier, by providing that a sliding sleeve, which is disposed in the rudder carrier and can be moved rearwardly by gas pressure and/or spring force, presses against pivot levers eccentrically mounted to the fins.

The present invention also contemplates improved rocket and projectile features usuable in other kinds of projectiles and rockets.

In DAS (German Published Application) No. 1,198,248, a control flap unit is described for projec tiles or rockets which can be fired from the barrel of a gun. wherein the rudder carrier has a longitudinal bore wherein a sliding sleeve is disposed which can be moved axially by means of a spring force. This sliding sleeve presses, with its rear end. against pivot or rotary levers eccentrically arranged at the rudders and thus unfolds, after the projectile or rocket has left the gun barrel, the fins about axes extending at right angles to the longitudinal axis of the projectile or the rocket, tangentially to the rudder carrier, into the flying position. It has also been contemplated to move the sliding sleeve rearwardly, instead of by spring force, or also additionally thereto, with the aid of the pressure of the powder gases of the firing propellant charge entering the rudder carrier during the firing of the projectile or rocket.

For packaging reasons and in order to facilitate the introduction of the projectile or rocket into the barrel of the gun, it is advantageous to keep the fins folded back against the rudder carrier until firing. This is accomplished, for example, in accordance with DOS (German Unexamined Published Application) No. l,428,669, by means of a ring pushed over the fins of the rudder, which ring is stripped off the fins and is pushed into a groove when the projectile or rocket enters the gun barrel. Such a construction, however, has the basic disadvantage that, after the projectile or rocket has perhaps been again unloaded or removed from the barrel and placed back into the transport package, the ring must again be pushed by hand over the fins, which consequently is cumbersome and undesirable during practical use in the armed forces.

The present invention is based in part on solving the problem of avoiding this above-discussed disadvantage by constructing a projectile or rocket with an unfoldable tail unit in such a manner that the fins can unfold only after the firing has actually taken place.

This invention contemplates, for a projectile or a rocket with hinged tail unit of the type mentioned in the foregoing, providing the sliding sleeve with an external annular groove in which the pivot levers engage with their free ends; and holding the sliding sleeve in a position wherein it arrests the fins in the folded condition by means of a connection with the rudder carrier which connection can be released at a predetermined instant during firing. According to one embodiment of the present invention, the sliding sleeve is held in its arresting position, for example. by means of two shear pins which, radially opposed to each other, are arranged in a bore penetrating the wall of the rudder carrier and the sliding sleeve. The strength of the shear pins is dimensioned so that they are sheared off during the firing of the projectile or rocket during the acceleration phase due to the sliding sleeve which is pressed rearwardly because of its mass moment of inertia and due to a compression spring which is preferably disposed in front thereof. In this construction of the control flap unit according to the invention, an additional auxiliary means for holding down the fins, and operable by hand, is not required. The fins remain folded until the actual firing and can unfold only when the shear pins have been separated due to the accelerative forces and the projectile or rocket has left the gun barrel. This ensures advantageously a rapid and reliable repeated loading and unloading of the projectile or rocket, as well as the possibility of placing the projectile or rocket back into the packaging container.

The free ends of the pivot levers engaging the annular groove generally have some axial play therein. In order to keep the frictional resistances during the unfolding of the fins at a minimum, the sliding sleeve of the present invention is arrested within the rudder carrier preferably so that it contacts, with the rear annular surface of its annular groove, more or less uniformly the pivot levers, in order to extensively inhibit the minor pivotal motions of the fins in the folded condition which could otherwise occur because of the axial play of the pivot levers in the annular groove.

In the just-described construction, and in the control flap until of the prior art discussed above, under certain unfavorable launching conditions. the compressive or pressure forces exerted during the acceleration phase by the sliding sleeve on the pivot levers of the fins may bend the pivot levers to a greater or less extent or cause damage to the edges of the sliding sleeve contacting the pivot levers. These pressure forces result from the mass moments of inertia of the sliding sleeve and of a compression spring which may be disposed in front of the sliding sleeve. This danger is increased even more by the fact that, in most cases, not all pivot levers contact the sliding sleeve initially in a uniform manner, due to the manufacturing tolerances which are unavoidable in mass production. Such damage, however, can ensue in a nonuniform unfolding of the fins and thus a reduction in the target accuracy of the projectile or rocket.

In order to avoid this last-mentioned disadvantage. a suitable embodiment of the present invention provides that the sliding sleeve is extended toward the rear with a preferably annular-cylindrical extension, and rests with the latter on a disk detachably arranged in the zone of the rear end of the rudder carrier. In one embodiment of this invention, the disk is threadedly connected from the rear in the rudder carrier and is equipped, for example, with an annular predetermined breaking zone, where the disk is severed under the effect of the powder gases of the propellant firing charge. The severed zone of the disk retains its position wherein it supports the sliding sleeve and an optionally provided compression spring until the projectile or rocket has exited from the gun barrel. After leaving the gun barrel the powder gases of the propellant firing charge no longer exert a forwardly directed pressure force on the disk. The severed zone of the disk can then be ejected toward the rear, and the sliding sleeve can move toward the rear, thus unfolding the fins of the rudder. With such an arrangement. the objective is advantageously attained that the sliding sleeve and the possibly provided compression spring are supported in the bottom or base of the projectile or rocket. so that the pivot levers of the fins, furing firing, are not stressed by the inertia forces of the sliding sleeve and the possibly provided compression spring. As was found in prac tice, the target accuracy could thereby be substantially increased.

In order to keep the friction during the movement of the sliding sleeve in the longitudinal bore of the rudder carrier at a minimum. a further suggestion of this inven' tion provides to construct the sliding sleeve with at least two spaced-apart external ring flanges to guide the sleeve within the rudder carrier such that the contact between the sliding sleeve and the rudder carrier is limited to relatively narrow annular areas. In accordance with another suggestion of this invention, one of the annular flanges is associated with the annular groove of the sliding sleeve so that the rear annular surface of this one annular flange is simultaneously the front lateral face of the annular groove so as to transmit the compressive forces exerted by the sliding sleeve on the pivot levers during the unfolding of the fins in a maximally favorable manner.

The powder gases of the propellant firing charge entering the interior of the rudder carrier during the firing of the projectile or rocket and flowing around the sliding sleeve. pivot lever. etc.. are under a considerable pressure, so that considerable flow velocities can occur in dependence on the respective throughflow cross sections. Under favorable conditions, this phenomenon can cause function-impairing erosions at the sliding sleeve, the pivot levers, the tail unit or rudders, etc., especially if these parts are made of aluminum, for example. In order to avoid this effect. the present invention contemplates providing the sliding sleeve with radial pressure-compensating openings. The throughflow cross sections of these openings are dimensioned in accordance with the conditions of the respective individual case so that erosions due to maximally high flow velocities can be reliably prevented. In addition thereto. or in place thereof. the annular flanges can also be provided with axial pressure-equalizing apertures, in accordance with another suggestion of the present invention.

In case it would be disadvantageous. for example. in embodiments with rudder fins manufactured of a synthetic resin, for the hot powder gases of the propellant firing charge flowing around the sliding sleeve to be discharged toward the outside through the circular-arcshaped slots formed in the rudder carrier for the pivot levers, and to flow around the fins. the further provi sion is made. according to this invention, to seal the sliding sleeve with respect to the zone of the rudder carrier which has the cutouts for the pivot levers by means of sealing elements disposed between the sleeve and the rudder carrier.

In order to reduce the friction and contact corrosion between the compression spring and the sliding sleeve in embodiments utilizing a compression spring to assist in forcing the sliding sleeve rearwardly. a further suggestion of this invention provides that the compression spring rests. with its rear end. under the interposition of an annular disk of preferably steel or polytetrafluoroethylene. against the front annular flange. This annular disk accommodates the minor rotational displacement between the spring and sleeve during thc fin unfolding process.

As indicated above, the detachable connection between the sliding sleeve and the rudder carrier can be a disk. the central portion of which. supporting the sliding sleeve. can be severed by way of an annular predetermined rupturing zone. The disk can also be held by means of shear pins or the like, which release the disk at a predetermined load or stress according to further embodiments contemplated by the present invention. These arrangements, of the disk connecting means however, are not fully satisfactory for all situations, since high expenditure has to be incurred in mass production in order to form these connecting elements so that the connection can always be broken in the same. definite manner. For example. if the predetermined breaking zone is manufactured with irregularities so that it also ruptures inaccurately. then the disk can jam while being flung out of the rear end of the rudder carrier. and thereby exert improper transverse forces on the projectile or rocket. As a consequence thereof. pendulating movements are created which impair the target accuracy and, in case of adverse circumstances. can even be the cause of ricochets.

In order to avoid this just-described disadvantage. the present invention contemplates further embodiments with the disk inserted in the rear end of the rudder carrier such that it rests in the forward direction against a shoulder formed interiorly at the rudder carrier and is held in this position by means of a tubular member arranged behind the disk. This tubular member contacts with its front edge an annular step of the disk and is firmly joined in its rear area with the rudder carrier. leaving an annular cavity between its front zone and the rudder carrier. which latter is formed with an inside cross section that is enlarged as compared to the cross section of the disk. Under the pressure effect of the powder gases of the propellant firing charge the front zone of the tubular member. which is. for example, of a conical shape. is pressed outwardly against the inner wall of the rudder carrier and partly into the annular cavity. whereby the front edge of the tubular member slides off the disk. thus releasing the disk along its entire periphery in a uniform manner. The disk can then be ejected toward the rear unimpeded.

The present invention contemplates use of this type of disk mounting with the tubular member not only when the disk serves for arresting a sliding sleeve. but advantageously also in all those cases wherein movable parts (such as the disk) are to be released upon reaching a certain gas pressure. For example. this is the case with a rocket which can be fired from a gun barrel and wherein the propellant powder charge of the cruising engine is ignited by the powder gases of the launching charge disposed behind the rocket. in such a rocket constructed in accordance with the present invention. a disk is arranged in the bottom of the rocket. which disk rests in a centering means and has a continuous, axially disposed bore which throttles the pressure of the powder gases of the launching propellant charge to the lower ignition pressure required for igniting the cruising engine. This disk must also be held in the bottom of the rocket until firing time whether or not a sliding sleeve for controlling pivot levers at rudder fins is present. and must be ejected toward the rear, unimpeded, only after the rocket has left the barrel to facilitate cruise operation of the cruising engine. Consequently. one can make use advantageously of the disk mounting according to the present invention by means of the w bular member which is tapered in the front zone thereof for the formation of the outer cavity, i.e. which is reduced in cross section. A throttle disk held in this manner can be used, for example, together with a control flap unit, the fins of which are held in the folded condition by means of a ring pushed thereover. However, it is particularly advantageous to utilize this throttle disk simultaneously for the arresting of the fins according to an embodiment of the present invention The disk mounting of this invention is constructed so that the disk, when a certain excess pressure occurs within the tubular member, is uniformly released. In order to obtain uniform results for volume produced rockets, maximally low pressure should be ambient in the annular cavity outside of the tubular member. In other words, the disk and the tubular member are to be inserted into the rear end of the rudder carrier so that as long as the tubular member hasnot yet freed the disk practically no powder gases of the propellant firing charge, or at least only a very minor amount, can enter into the outer annular cavity. in order to improve this seal of the outer cavity, a further suggestion of the invention resides in that the rudder carrier is formed with a continuous edge on the inside at the transition from the zone receiving the disk to the zone receiving the tubular member. The tubular member can then be pressed against this edge with the outer surface of its front area. In this connection, the tubular member can either initially contact this edge, or can be expanded to a minor extent for contacting purposes under the effect of the powder gas pressure of the propellant firing charge and can then be pressed against this edge. In any event, an additional seal of the outer cavity is thus attained, in that, during the pressure rise in the tubular member, the latter is pressed against the edge of the rudder carrier and, only after reaching a certain pressure buildup, is pressed toward the outside into the cavity disposed therebehind while sliding with its front zone along this edge. A further improvement of the seal for the cavity can also be obtained, according to this invention, by providing that the disk is supported on the annular shoulder ofthe rudder carrier by means of an annular sealing strip or gasket.

According to one embodiment contemplated by the present invention, the tubular member is fixedly connected with the rudder carrier with its rear zone basically by being inserted therein with a press fit. However, if this frictional connection should be insufficient, in individual cases, for reliably absorbing the axial forces exerted by the powder gas of the propellant firing charge on the front zone of the tubular member, then, in accordance with another proposal of this invention, the tubular member can be glued with its rear zone into the rudder carrier, for example by means ofa two component or dual adhesive on the basis of an epoxy resin. Additionally, or also in place thereof, another suggestion of the invention provides a shape-mating connection between the tubular member and the rudder carrier, in that the tubular member engages, with its rear edge which is beaded on the outside preferably by flanging, into a corresponding annular groove disposed on the inside of the rudder carrier.

The projectile or rocket according to this invention is preferably utilized with a hollow-charge warhead. in order to initiate the hollow charge upon impact of the projectile or rocket, it has been contemplated to dispose, in the rear of the projectile or rocket. a piezoelectric percussion or impact detonator or fuzc. According to the present invention, the provision is made, in this connection, to retain the percussion detonator with the interposition of a spring element, preferably including at least one cup spring, between the threadedly connected front and rear portions of the projectile rear or rocket tail. The divided construction of the rear section according to this invention makes it possible to make do without special mounting elements for the impact detonator, such as, for example, screws or synthetic resin housings, while the interposed spring element ensures that the impact detonator, in spite of the usual manufacturing tolerances, is pressed sufficiently firmly against the bottom of the recess which receives the det onator. Consequently, the shock piezoelectric produced during impact of the projectile or rocket in the hollow-charge head is reliably transmitted to the peizoelectric element and produces the ignition voltage at that point.

The combustion chamber of the cruising engine of the rocket according to this invention is to be sealed off from outside influences, such as water, for example. This seal must also withstand mechanical stresses, for example due to shocks during transport or ejection from a supply plane. However, the flawless ignition of the cruising engine by means of the powder gases ofthe propellant firing charge must not be impaired, either, in a temperature range of, for example, 40 C. to +50 C. Also, portions of the seal must not result in clogging of the nozzle. According to the invention, the provision is made, therefore, for this purpose to cover the inside cross section of the nozzle with a thin disk or foil of a metal or a synthetic resin which can be ruptured by the powder gases. This disk or foil is preferably disposed downstream of the narrowest nozzle cross section as seen in the flow direction.

The zone of the narrowest nozzle cross section is exposed to strong thermal and mechanical stresses, due to the very rapidly flowing hot powder gases. It has been contemplated to accommodate these stresses by producing the nozzle section having the narrowest cross section as a separate part from a more rugged material, such as, for example, steel or graphite, and then inserting this nozzle section into a special nozzle carrier of aluminum, for example. In this case, the disk or foil of the present invention can be advantageously clamped between the nozzle carrier and the nozzle inserted therein. In case a disk or foil is used made ofa synthetic resin, it is advantageous, with a view toward the required proofness to water vapor or steam-proofness, to deposit on one side thereof a metal, such as aluminum, for example, by vaporization.

Rockets which can be fired from a gun barrel are subject, in contrast to the usual rockets, to considerable accelerations which can amount to up to about 7,000 g. s (g. gravity force). If the cruising engine is to be ignited by the powder gases of the propellant firing charge, there is the problem to arrange the ignition charge for the cruising engine so that it will still be reliably ignited by the powder gases of the propellant firing charge at temperatures of, for example 40C., on the one hand, and so that the detonator is not destroyed, on the other hand. due to the very strong acceleration forces during firing or is otherwise impaired in its flawless operation. According to this invention, it is furthermore provided, for this purpose, to hold the ignitor or ignition charge in a housing fixedly disposed on the side of the combustion chamber opposite the nozzle and 7 being perforated like a sieve in the zone of the ignition charge. The housing is suitably provided with a cupshaped indentation wherein the ignition charge. formed in the shape of a pellet. is securely held.

A particularly simple and suitable mounting of the housing can be obtained by clamping the housing between the front end wall of the combustion chamber and the flame-inhibiting casing of the solid propellant of the cruising engine.

These and further objects. features and advantages of the present invention will become more obvious from the following description when taken in connection with the accompanying drawings which show. for purposes of illustration only. several embodiments in accordance with the present invention.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. I is a part sectional side view of a rocket constructed in accordance with the present invention which is inserted in a gun barrel;

FIG. 2 is a cross-sectional side view of a part of the rocket of FIG. 1 which illustrates the rear end of the rudder carrier with the sliding sleeve;

FIGS. 3 and 4 are views similar to FIG. 2 which show two modifications of the present invention with differently shaped sliding sleeves;

FIG. 5 is a schematic partially cross-sectional side view of a part of the rocket of FIG. I which illustrates the rear end of the rudder carrier with unfolded fins;

FIG. 6 is an enlarged cross-sectional side view which shows the disk mounting at the rear end of the rudder carrier in accordance with the present invention;

FIG. 7 is a partial cross-sectional side view of a front part of the rocket of FIG. I which shows the mounting of the impact detonator;

FIG. 8 is a partial cross-sectional side view illustrating details of the modified cruising engine constructed in accordance with the present invention;

FIG. 9 is a cross-sectional side view of part of the rocket of FIG. I which shows the mounting of the ignition charge; and

FIG. I0 is an end sectional view which shows the housing for the ignition charge for the rocket of FIG. 1.

DETAILED DESCRIPTION OF THE DRAWINGS The rocket. inserted according to FIG. I in a gun barrel I from the front and being illustrated partially in section. has a nose 2, a tail or rear 3. a rudder carrier 4, and a propellant firing charge 5. The rudder carrier 4 is provided with a longitudinal bore 6 wherein an axially movable sliding sleeve 7 and a compression spring 8 are housed. At the rear end of the rudder carrier 4, fins 9 are attached with kingpins 10. In the FIG. 1 illustration. the fins 9 are folded against the rudder carrier 4. A pivot lever 11 is attached to each fin 9 at a spacing from the kingpins I0. Each of the pivot levers extends through respective circular-arc-shaped slots l2 in the rudder carrier 4 into the bore 6 thereof and. at that point. projects with a free end into annular groove 13 of the sliding sleeve 7. The axial play between the pivot lever II and the annular groove I3 is dimensioned so that the fins 9 are fixed or arrested to the required extent in the folded storage position of the fins. By means of an annulancylindrical extension 14. the sliding sleeve 7 rests on a disk 15 inserted in the rear end of the rudder carrier 4. The disk IS. in turn. is held by means of tubular member I6. Instead of the annular-cylindrical extension I4. it is also possible, according to other preferred embodiments of the invention, to employ, for example. three rod-like projections extending in the longitudinal direction which are disposed so that they are uniformly distributed along the periphery of the sliding sleeve 7. A casing 17 of a propellant firing charge 5 is separated during firing in a conventional manner from the rudder carrier 4 and thus from the rocket leaving the gun barrel I. This separation of the casing 17 and carrier takes place in the zone of the coupling element 18. Solid propellant charge I9 of the cruising engine and the cruising engine nozzle 20 are arranged in the tail 3 of the rocket.

In FIG. 2, the sliding sleeve 7 is shown on an enlarged scale. The sliding sleeve 7 is guided in the bore 6 of the rudder carrier 4 by means of two narrow annular flanges ZI, 22. At the front end. the sliding sleeve 7 has an annular-cylindrical extension 23 serving for the centering of the compression spring 8. Between the rear end of the compression spring 8 and the annular flange 21, an annular disk 24 preferably of steel or polytetrafluoroethylcne is disposed. With the rear extension 14, the sliding sleeve 7 rests against the disk I5. Directly behind the rear annular flange 22 is an annular groove 13; the rearward annular lateral surface 25 of the groove 13 contacts the pivot levers ll of the fins 9, whereas a small gap is provided between the front lateral surface 26 of the annular groove 13 and the pivot levers II. The spacing between the rear lateral surface 25 and the rear end face of the extension 14 is selected so that the fins 9, in the arrested or stored condition. are flawlessly in contact with the rudder carrier 4. Radial pressure-equalizing apertures 27 are provided in the extension 14 of the sliding sleeve 7. The disk 15, provided with a throttle bore 28, is pressed against the shoulder 29 of the rudder carrier 4 by means of tubular member 16.

FIG. 3 shows another embodiment which is similar to the FIG. 2 arrangement except that sliding sleeve 7' differs from sleeve 7 by including additional radial pressure-equalizing apertures 27 arranged in the zone between the annular flanges 21, 22, and axial pressureequalization bores 30 provided in the annular flanges 2], 22 proper.

FIG. 4 shows another embodiment which is similar to the FIG. 2 arrangement except that sliding sleeve 7" differs from the sliding sleeve 7 in that the sliding sleeve 7" is sealed by means of 0-seals or sealing rings or other sealing elements 31 at the front annular flange 21 and at the annular shoulder 29 of the rudder carrier 4 with respect to the zone of the rudder carrier 4 having the slots I2. The sliding sleeve 7" has no pressureequalizing apertures in this FIG. 4 embodiment.

The mode of operation of the arrangement of this invention upon firing is as follows:

After the ignition of the propellant firing charge 5 and the associated pressure increase in the firearm or gun, the tubular element 16 releases the disk 15. As long as the rocket is still within the gun barrel 1, the high pressure of the powder gases of the propellant firing charge 5 is effective on the disk 15 from the rear. A small portion of the powder gases flows through the throttle bore 28 into the bore 6 of the rudder carrier 4;

The sliding sleeve 7 rests on the disk I5 during the strong acceleration of the rocket and thus does not exert any stress on the pivot levers II of the fins 9. The gas dammed up in the bore 6 of the rudder carrier 4 can. in part. be discharged through the prcssure-equaL izing apertures 27, 30 in the sliding sleeve 7, 7' and through the slots [2 in the rudder carrier 4, or it is accumulated in the bore 6 of the rudder carrier 4 when using the scaled sliding sleeve 7". in which case the throttle bore 28 of the disk 15 can be of a somewhat smaller diameter. After the rocket has left the gun barrel I. the disk I5 falls off toward the rear. due to the powder gases dammed up in the bore 6. simultaneously upon rearward movement of disk IS. the sliding sleeve 7 is pushed rearwardly against the pivot levers I l of the fins 9 and thus presses the fins 9 into the flying position shown in FIG. 5. In FIG. 5. which shows the rear end of the rudder carrier 4 partially in a sectional view. only two of the fins 9, which can total. for example. six, are illustrated in order to simplify the drawing.

In FIG. 6, the mounting of the disk according to this invention is shown on an enlarged scale. The disk I5. which serves on the one hand for fixedly holding the sliding sleeve 7 and. on the other hand. for throttling the pressure of the powder gases of the propellant firing charge 5 to the ignition pressure of the cruising engine, rests with a sealing strip 32 at the shoulder 29 of the rudder carrier 4. The disk is held in this position by means of the tubular member 16 which is made of brass. for example. The tubular member 16 is conically tapered in its front zone 33 toward the disk I5 and rests with its front edge on the annular shoulder 34 of the disk 15. With its rear zone 35, the tubular member l6 engages the rudder carrier 4 and locks. with the outwardly flanged rear edge 36, into a corresponding annular groove 37 of the rudder carrier 4. Additionally or in place thereof. the provision can also be made to glue the tubular member 16 with its rear zone 35 to the rudder carrier 4. The axial forces effective on the tubular member l6 are absorbed by the flanged edge 36 and/or by the glue connection. The rudder carrier 4 is provided with a continuous edge 38 at the transition from the zone receiving the disk l5 to the zone receiving the tubular member l6. The tubular member 16 contacts this edge 38 with the outer wall ofits front zone 33. The dimensions are chosen so that the front zone of the tubular member 16 is only little removed from the edge 38. Preferably, this spacing is 0.1 to 0.5 mm. Depending on the strength of the tubular member 16 and the value of the pressure of the powder gases of the propellant firing charge 5. other dimensions can. however. also be selected in individual cases.

After the ignition of the propellant firing charge 5, the front zone 33 of the tubular member 16 is pressed against the edge 38 and thus the outer cavity 39 between the tubular member 16 and the wall of the rudder carrier 4 is additionally sealed off. When the pressure of the powder gases has risen to a predetermined value. the front zone 33 of the tubular member 16 is pressed into the cavity 39 as shown in FIG. 5 and thus releases the disk IS. A portion ofthe powder gases flows through the throttle bore 28 of the disk 15 into the combustion chamber of the cruising engine and there ignites the propellant charge [9 disposed thcrcat. After the rocket has left the gun barrel 1. the disk 15 as described above is ejected toward the rear so that the fins 9 of the tail unit can unfold into the flight posi tion.

According to FIG. 7. the projectile or rocket has a hollow-charge warhead with a hollow charge 40. a conical metal lining 41. and a hood 42. The front portion 43 of the tail 3 is connected with its rear portion 44 by means of the threaded connection 45. Between the two portions 43, 44. the piezoelectric impact detonator 46,

10 shown in a plan view. is held in a recess and is sufficiently firmly in engagement with the front end wall of the recess by means of the spring element 47. Thus. with low space requirement and low manufacturing expenditure. a secure contact is ensured between the detonator and the projectile or rocket.

In FIG. 8, the rocket is shown with its cruising engine in a longitudinal sectional view. The combustion chamber of the cruising engine with the solid propellant charge [9 disposed therein is sealed off from outside influences by the foil 48 held between the nozzle carrier 49 and the nozzle 50 inserted therein. (Nozzle carrier 49 and nozzle 50 correspond to the nozzle 2" of the Flg. l embodiment). The foil 48 is arranged as seen in the flow direction of the propellant gases of the cruising engine as closely as possible behind the narrowest nozzle cross section 5]. so that the free cross section of the foil is correspondingly small and thus the foil 48 is disintegrated only in relatively small fragments during the ignition of the cruising engine. which fragments do not lead to any clogging either in the nozzle 50 or in the zone of the compression spring 8 and sliding sleeve 7 of the rudder carrier 4 (sec FIGS. l-4 for details of spring 8 and sleeve 7). An advantageous foil is a self-adhesive foil or film of polyester of a thickness of 0.05 mm.. which has a coat of aluminum vaporized on both sides. At the front end ofthe solid propellant charge 19. which is an internally burning grain. the ignition charge 52 is arranged in the housing 53.

As shown in FIG. 9 on an enlarged scale. the ignition charge 52, fashioned as a pellet. is accommodated in the central cup-shaped indentation of the housing 53, pointing toward the nozzle side. in such a manner that it reliably withstands even greater accelerative forces. In order to make it possible for the ignition charge 52 to be ignited by the powder gases of the propellant firing charge 5, on the one hand. and to provide for the ignition of the solid propellant charge 19 by the ignition charge 52. on the other hand. the housing 53 is provided with sieve-like perforations 54 in the zone of the cup-shaped indentation. To facilitate the assembly and in view of the stresses during storage and transportation, the ignition charge 52 is held in the housing 53 by means of a paper disk 55 glued thereon. The housing 53 is held at the side of the combustion chamber oppositely to the nozzle by being clamped in between the end wall 56 of this chamber and the flame-inhibiting insulation 57 of the solid propellent charge [9. which insulation is made. for example. of ethylcellulose. The housing 53 serves advantageously at the same time for centering the solid propellant grain I9 within the combustion chamber. The housing furthermore provides the required pressure equalization between the interior of the solid propellant charge l9 and the gap 58 between the cylindrical insulation 57 and the wall of the combustion chamber. in that the housing is supported on the end wall of the combustion chamber by way of four axial extensions (lugs. projections) 59 arranged in a uniform distribution. between which the propellant gases can pass through and enter the gap 58.

Although the above-described and specifically illustrated embodiments of the present invention utilize the novel disk connection (FIG. 6). sliding sleeve for controlling folding fins (FIGS. 1-5). warhead detonator (FIG. 7). cruise engine and ignition means therefore (FIGS. 8-10) in conjunction with one another on the same rocket propelled projectile. the present invention also contemplates utilizing these novel features inde- 1 l pendently of one another on other rocket arrangements. However. the preferred illustrated embodiments relate to very advantageous utilization of a combination of these novel features opcratively interrelated to one another in a single rocket structure.

While we have shown and described only several embodiments in connection with the present invention. it is understood that the same is not limited thereto, but is susceptible to numbcrous changes and modifications as would be known to those skilled in the art given the present disclosure of the invention, and we therefore do not wish to be limited to the details shown and described herein only schematically but intend to cover all such changes and modifications.

We claim:

1. A projectile comprising:

rudder carrier means extending in the direction of a longitudinal axis of the projectile.

at least one guiding fin means attached to said rudder carrier means. each of said guiding fin means being movable about a respective fin pivot axis extending substantially perpendicularly to said longitudinal axis between a first storage position extending tangentially along the rudder carrier means and a second-in-flight position extending outwardly of said rudder carrier means.

pivot lever means mounted on each of said fin means eccentrically with respect to a respective fin pivot axis,

and sliding sleeve means carried by said rudder carrier means. said sliding sleeve means being provided with annular groove means having a front lat.- eral surface and a rear lateral surface for accommodating a free end of each pivot lever means. said sliding sleeve means being movable from a fin arresting position with said rear lateral surface engaging said pivot lever means to hold said fin means in said first position to positions with said front lateral surface engaging said pivot lever means to move said fin means to said second position.

2. A projectile comprising:

rudder carrier means extending in the direction of a longitudinal axis of the projectile.

at least one guiding fin means attached to said rudder carrier means. each of said guiding fin means being movable about a respective fin pivot axis extending substantially perpendicularly to said longitudinal axis between a first storage position extending tangentially along the rudder carrier means and a second iii-flight position extending outwardly of said rudder carrier means.

pivot lever means mounted on each of said fin means eccentrically with respect to a respective fin pivot axis.

and sliding sleeve means carried by said rudder carrier means and having annular groove means for accommodating a free end of each pivot lever means. and sliding sleeve means being movable from a fin arresting position with said groove means engaging said pivot lever means to hold said fin means in said first position to positions with said groove means engaging said pivot lever means to move said fin means to said second position. whereby retention of said sliding sleeve means in said fin arresting position is accommodated, wherein said sliding sleeve means is held in said fin arresting position by connecting means interposed between said rudder carrier means and said sliding sleeve means. and wherein connection release means are provided for releasing said connecting means at a predetermined instant during launching of the projectile. 5 3. A projectile according to claim 2. wherein said sliding sleeve means is held in a forward position by said connecting means. and wherein at least one of spring force means and gas pressure force means are arranged in said rudder carrier means to move said sliding sleeve means in a rearward direction upon release of said connecting means.

4. A projectile according to claim 3. wherein said sliding sleeve means is mounted inside of said rudder carrier means. and wherein said aannular groove means faces radially outwardly with respect to said longitudi nal axis.

5. A projectile according to claim 3, wherein said connecting means includes a disk detachably connected adjacent the rear end of the rudder carrier means, and wherein said sliding sleeve means includes an annular rearward extension which rests on said disk when said sliding sleeve means is in said first position.

6. A projectile according to claim 3, wherein said sliding sleeve means is disposed inside of said rudder carrier means and includes at least two spaced-apart external annular flanges for slidably guiding said sliding sleeve means in said rudder carrier means.

7. A projectile according to claim 5, wherein said sliding sleeve means is disposed inside of said carrier means and includes at least two spacedapart external annular flanges for slidably guiding said sliding sleeve means in said rudder carrier means.

8. A projectile according to claim 6, wherein a rearwardly facing annular surface of one of said annular flanges simultaneously serves as a front lateral surface of the groove means. said front lateral surface of the groove means being spaced forwardly from said pivot lever means when said sliding sleeve means is in said first position and being in engagement with said pivot lever means when said sliding sleeve means is in said second position.

9. A projectile according to claim 7, wherein a rearwardly facing annular surface of one of said annular flanges simultaneously serves as a front lateral surface of the groove means, said front lateral surface of the groove means being spaced forwardly from said pivot lever means when said sliding sleeve means is in said first position and being in engagement with said pivot lever means when said sliding sleeve means is in said second position.

10. A projectile according to claim 6. wherein said sliding sleeve means is provided with radially extending pressure equalizing apertures.

11. A projectile according to claim 9, wherein said sliding sleeve means is provided with radially extending pressure equalizing apertures.

12. A projectile according to claim 6. wherein said sliding sleeve means is provided with axially extending pressure equalizing bores.

13. A projectile according to claim ll, wherein said sliding sleeve means is provided with axially extending pressure equalizing bores.

14. A projectile according to claim 6, wherein said rudder carrier means is provided with cutouts for accommodating said pivot lever means. and wherein sealing elements are arranged between the sliding sleeve means and the rudder carrier means for sealing off the sliding sleeve means from the zone of said cutouts.

15. A projectile according to claim 9, wherein said rudder carrier means is provided with cutouts for accommodating said pivot lever means, and wherein sealing elements are arranged between the sliding sleeve means and the rudder carrier means for sealing off the sliding sleeve means from the zone of said cutouts.

16. A projectile according to claim 6, wherein compression spring means are arranged in said projectile with a rear end thereof resting at the most forward of said annular flanges with the interposition of an annular disk constructed on one of steel and polytetrafluorethylene.

17. A projectile according to claim 9, wherein compression spring means are arranged in said projectile with a rear end thereof resting at the most forward of said annuar flanges with the interposition of an annular disk constructed of one of steel and polytetrafluorethylene.

18. A projectile according to claim 5, wherein a forward end of said disk contacts an interiorly formed shoulder of said rudder carrier means, wherein said disk is held in position against said shoulder by a tubular member disposed rearwardly of the disk, wherein a rear end portion of said tubular member is fixedly joined to said rudder carrier means and a forward end portion of said tubular member is in abutting engagement with a rearwardly facing annular shoulder of said disk while leaving an annular cavity between a forward zone of the tubular member and the rudder carrier means, and wherein said cavity is formed with an inside cross section which is radially outwardly of the cross section of said disk for accommodating portions of said tubular member upon release of said disk at said predetermined instant during launching of the projectile.

19. A projectile according to claim 9, wherein a forward end of said disk contacts an interiorly formed shoulder of said rudder carrier means, wherein said disk is held in position against said shoulder by a tubular member disposed rearwardly of the disk, wherein a rear end portion of said tubular member is fixedly joined to said rudder carrier means and a forward end portion of said tubular member is in abutting engagement with a rearwardly facing annular shoulder of said disk while leaving an annular cavity between a forward zone of the tubular member and the rudder carrier means. and wherein said cavity is formed with an inside cross section which is radially outwardly of the cross section of said disk for accommodating portions of said tubular member upon release of said disk at said predetermined instant during launching of the projectile.

20. A projectile according to claim 18, wherein the rudder carrier means has a continuous annular edge portion on the inside adjacent the forward end portion of the tubular member and the rearward end of the disk. and wherein an outer surface portion of said tubular member is pressed against said annular edge portion in the assembled condition of said disk and tubular member.

21. A projectile according to claim 20, wherein said annular edge portion is disposed between and immediately adjacent said annular cavity and said rearwardly facing annular shoulder of said disk in the assembled condition of said disk and tubular member such that the portion of the tubular member which is forward of 14 said annular edge portion may be pressed into said annular cavity to permit release of said disk in the rearward direction.

22. A projectile according to claim 18, wherein a ring-shaped sealing strip is interposed between said interiorly formed shoulder of said rudder carrier means and said forward end of said disk.

23. A projectile according to claim 21, wherein a ring-shaped sealing strip is interposed between said in teriorly formed shoulder of said rudder carrier means and said forward end of said disk.

24. A projectile according to claim 18, wherein said rear end portion of said tubular member is glued to said rudder carrier means.

25. A projectile according to claim 23, wherein said rear end portion of said tubular member is glued to said rudder carrier means.

26. A projectile according to claim 18, wherein said rear end portion of said tubular member is provided with an annular bead portion which is fixedly engaged in a corresponding annular groove provided on the in side of the rudder carrier means.

27. A projectile according to claim 25, wherein said rear end portion of said tubular member is provided with an annular bead portion which is fixedly engaged in a corresponding annular groove provided on the inside of the rudder carrier means.

28. A projectile according to claim I, further comprising a piezoelectric impact detonator. wherein said projectile is formed of detachably connected front and rear sections. and wherein said impact detonator is held in position between said front and rear sections by resilient means.

29. A projectile according to claim 28, wherein said front and rear sections are threadedly connected. and wherein said resilient means includes at least one cup spring.

30. A projectile according to claim 5, further comprising a piezoelectric impact detonator. wherein said projectile is formed of detachably connected front and rear sections, and wherein said impact detonator is held in position between said front and rear sections by resilient means.

31. A projectile according to claim 8, further comprising a piezoelectric impact detonator. wherein said projectile is formed of detachably connected front and rear sections. and wherein said impact detonator is held in position between said front and rear sections by resilient means.

32. A projectile according to claim 31, wherein said impact detonator is arranged forwardly of said sliding sleeve means.

33. A projectile according to claim 2, wherein said connecting means include shear pin means arranged in radially extending bores of the rudder carrier means and sliding sleeve means.

34. A projectile according to claim 5, wherein said disk is threadedly connected to the rear of the rudder carrier means and includes an annular predetermined breaking zone where the disk is severed under the effect of powder gases from a propellant firing charge disposed rearwardly of the disk. 

1. A projectile comprising: rudder carrier means extending in the direction of a longitudinal axis of the projectile, at least one guiding fin means attached to said rudder carrier means, each of said guiding fin means being movable about a respective fin pivot axis extending substantially perpendicularly to said longitudinal axis between a first storage position extending tangentially along the rudder carrier means and a second-in-flight position extending outwardly of said rudder carrier means, pivot lever means mounted on each of said fin means eccenTrically with respect to a respective fin pivot axis, and sliding sleeve means carried by said rudder carrier means, said sliding sleeve means being provided with annular groove means having a front lateral surface and a rear lateral surface for accommodating a free end of each pivot lever means, said sliding sleeve means being movable from a fin arresting position with said rear lateral surface engaging said pivot lever means to hold said fin means in said first position to positions with said front lateral surface engaging said pivot lever means to move said fin means to said second position.
 2. A projectile comprising: rudder carrier means extending in the direction of a longitudinal axis of the projectile, at least one guiding fin means attached to said rudder carrier means, each of said guiding fin means being movable about a respective fin pivot axis extending substantially perpendicularly to said longitudinal axis between a first storage position extending tangentially along the rudder carrier means and a second in-flight position extending outwardly of said rudder carrier means, pivot lever means mounted on each of said fin means eccentrically with respect to a respective fin pivot axis, and sliding sleeve means carried by said rudder carrier means and having annular groove means for accommodating a free end of each pivot lever means, and sliding sleeve means being movable from a fin arresting position with said groove means engaging said pivot lever means to hold said fin means in said first position to positions with said groove means engaging said pivot lever means to move said fin means to said second position, whereby retention of said sliding sleeve means in said fin arresting position is accommodated, wherein said sliding sleeve means is held in said fin arresting position by connecting means interposed between said rudder carrier means and said sliding sleeve means, and wherein connection release means are provided for releasing said connecting means at a predetermined instant during launching of the projectile.
 3. A projectile according to claim 2, wherein said sliding sleeve means is held in a forward position by said connecting means, and wherein at least one of spring force means and gas pressure force means are arranged in said rudder carrier means to move said sliding sleeve means in a rearward direction upon release of said connecting means.
 4. A projectile according to claim 3, wherein said sliding sleeve means is mounted inside of said rudder carrier means, and wherein said aannular groove means faces radially outwardly with respect to said longitudinal axis.
 5. A projectile according to claim 3, wherein said connecting means includes a disk detachably connected adjacent the rear end of the rudder carrier means, and wherein said sliding sleeve means includes an annular rearward extension which rests on said disk when said sliding sleeve means is in said first position.
 6. A projectile according to claim 3, wherein said sliding sleeve means is disposed inside of said rudder carrier means and includes at least two spaced-apart external annular flanges for slidably guiding said sliding sleeve means in said rudder carrier means.
 7. A projectile according to claim 5, wherein said sliding sleeve means is disposed inside of said carrier means and includes at least two spaced-apart external annular flanges for slidably guiding said sliding sleeve means in said rudder carrier means.
 8. A projectile according to claim 6, wherein a rearwardly facing annular surface of one of said annular flanges simultaneously serves as a front lateral surface of the groove means, said front lateral surface of the groove means being spaced forwardly from said pivot lever means when said sliding sleeve means is in said first position and being in engagement with said pivot lever means when said sliding sleeve means is in said second position.
 9. A projectile according to claim 7, wherein a rearwardly facing annular surface of one of said annular flanges simultaneously serves as a front lateral surface of the groove means, said front lateral surface of the groove means being spaced forwardly from said pivot lever means when said sliding sleeve means is in said first position and being in engagement with said pivot lever means when said sliding sleeve means is in said second position.
 10. A projectile according to claim 6, wherein said sliding sleeve means is provided with radially extending pressure equalizing apertures.
 11. A projectile according to claim 9, wherein said sliding sleeve means is provided with radially extending pressure equalizing apertures.
 12. A projectile according to claim 6, wherein said sliding sleeve means is provided with axially extending pressure equalizing bores.
 13. A projectile according to claim 11, wherein said sliding sleeve means is provided with axially extending pressure equalizing bores.
 14. A projectile according to claim 6, wherein said rudder carrier means is provided with cutouts for accommodating said pivot lever means, and wherein sealing elements are arranged between the sliding sleeve means and the rudder carrier means for sealing off the sliding sleeve means from the zone of said cutouts.
 15. A projectile according to claim 9, wherein said rudder carrier means is provided with cutouts for accommodating said pivot lever means, and wherein sealing elements are arranged between the sliding sleeve means and the rudder carrier means for sealing off the sliding sleeve means from the zone of said cutouts.
 16. A projectile according to claim 6, wherein compression spring means are arranged in said projectile with a rear end thereof resting at the most forward of said annular flanges with the interposition of an annular disk constructed on one of steel and polytetrafluorethylene.
 17. A projectile according to claim 9, wherein compression spring means are arranged in said projectile with a rear end thereof resting at the most forward of said annuar flanges with the interposition of an annular disk constructed of one of steel and polytetrafluorethylene.
 18. A projectile according to claim 5, wherein a forward end of said disk contacts an interiorly formed shoulder of said rudder carrier means, wherein said disk is held in position against said shoulder by a tubular member disposed rearwardly of the disk, wherein a rear end portion of said tubular member is fixedly joined to said rudder carrier means and a forward end portion of said tubular member is in abutting engagement with a rearwardly facing annular shoulder of said disk while leaving an annular cavity between a forward zone of the tubular member and the rudder carrier means, and wherein said cavity is formed with an inside cross section which is radially outwardly of the cross section of said disk for accommodating portions of said tubular member upon release of said disk at said predetermined instant during launching of the projectile.
 19. A projectile according to claim 9, wherein a forward end of said disk contacts an interiorly formed shoulder of said rudder carrier means, wherein said disk is held in position against said shoulder by a tubular member disposed rearwardly of the disk, wherein a rear end portion of said tubular member is fixedly joined to said rudder carrier means and a forward end portion of said tubular member is in abutting engagement with a rearwardly facing annular shoulder of said disk while leaving an annular cavity between a forward zone of the tubular member and the rudder carrier means, and wherein said cavity is formed with an inside cross section which is radially outwardly of the cross section of said disk for accommodating portions of said tubular member upon release of said disk at said predetermined instant during launching of the projectile.
 20. A projectile according to claim 18, wherein the rudder carrier means has a continuous annular edge portion on the inside adjacent the forward end portion of the tubular member and the rearward end of thE disk, and wherein an outer surface portion of said tubular member is pressed against said annular edge portion in the assembled condition of said disk and tubular member.
 21. A projectile according to claim 20, wherein said annular edge portion is disposed between and immediately adjacent said annular cavity and said rearwardly facing annular shoulder of said disk in the assembled condition of said disk and tubular member such that the portion of the tubular member which is forward of said annular edge portion may be pressed into said annular cavity to permit release of said disk in the rearward direction.
 22. A projectile according to claim 18, wherein a ring-shaped sealing strip is interposed between said interiorly formed shoulder of said rudder carrier means and said forward end of said disk.
 23. A projectile according to claim 21, wherein a ring-shaped sealing strip is interposed between said interiorly formed shoulder of said rudder carrier means and said forward end of said disk.
 24. A projectile according to claim 18, wherein said rear end portion of said tubular member is glued to said rudder carrier means.
 25. A projectile according to claim 23, wherein said rear end portion of said tubular member is glued to said rudder carrier means.
 26. A projectile according to claim 18, wherein said rear end portion of said tubular member is provided with an annular bead portion which is fixedly engaged in a corresponding annular groove provided on the inside of the rudder carrier means.
 27. A projectile according to claim 25, wherein said rear end portion of said tubular member is provided with an annular bead portion which is fixedly engaged in a corresponding annular groove provided on the inside of the rudder carrier means.
 28. A projectile according to claim 1, further comprising a piezoelectric impact detonator, wherein said projectile is formed of detachably connected front and rear sections, and wherein said impact detonator is held in position between said front and rear sections by resilient means.
 29. A projectile according to claim 28, wherein said front and rear sections are threadedly connected, and wherein said resilient means includes at least one cup spring.
 30. A projectile according to claim 5, further comprising a piezoelectric impact detonator, wherein said projectile is formed of detachably connected front and rear sections, and wherein said impact detonator is held in position between said front and rear sections by resilient means.
 31. A projectile according to claim 8, further comprising a piezoelectric impact detonator, wherein said projectile is formed of detachably connected front and rear sections, and wherein said impact detonator is held in position between said front and rear sections by resilient means.
 32. A projectile according to claim 31, wherein said impact detonator is arranged forwardly of said sliding sleeve means.
 33. A projectile according to claim 2, wherein said connecting means include shear pin means arranged in radially extending bores of the rudder carrier means and sliding sleeve means.
 34. A projectile according to claim 5, wherein said disk is threadedly connected to the rear of the rudder carrier means and includes an annular predetermined breaking zone where the disk is severed under the effect of powder gases from a propellant firing charge disposed rearwardly of the disk. 